Similarly shaped airfoils to NACA63-609 a=0.8
New! Bulk download of polars in Excel format: NACA63-609%20a%3D0.8.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
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2. NACA63-709
3. NACA64-709
4. NACA63A609
5. NACA64A609
6. NACA65-609 a=0.8
7. HQ 3.5/9
8. NACA65-709
9. NACA63-610 a=0.8
10. NACA64-610 a=0.8
11. NACA63-609 a=0.6
12. NACA64-609 a=0.6
13. DAE-51
14. NACA63-710
15. NACA64-710
16. NACA65A609
17. GOE 602 MOD.
18. SD7043 (9.1%)
19. HQ 3.5/8
20. MH 38 9.68%
21. NACA65-609 a=0.6